TYPE-CERTIFICATE DATA SHEET

Transcription

1 TYPE-CERTIFICATE DATA SHEET No. IM.E.053 for CF34-8 series engines Certificate Holder General Electric Aircraft Engines GE Aviation 1000 Western Avenue Lynn, Massachusetts USA For Models: CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 CF34-8C5A3 CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E6 CF34-8E6A1 TE.TC European Aviation Safety Agency, All rights reserved. Proprietary document. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

2 Intentionally left blank TE.CERT European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 2 of 20

3 TABLE OF CONTENTS I. General / Models: Certificate Holder Manufacturer Date of Application Validation Reference Date: EASA Certification Date... 4 II. Certification Basis FAA Certification Basis details: EASA Certification Basis: Airworthiness Standards: Special Conditions: Equivalent safety finding: Deviations: EASA environmental protection requirements:... 5 III. Technical Characteristics Design Definition Description Equipment Dimensions Dry Weight Ratings Control System Fluids (Fuel, Oil, Coolant, Additives) Fuel: Oil: Aircraft Accessory Drives Permissible Air Bleed Extraction: (See Note 5) IV. Operating Limitations Temperature Limits Exhaust Gas Temperature C ( F): Oil Temperature (measured in the oil tank) C ( F): Fuel Inlet Temperature (at engine fuel filter inlet) C ( F): Permissible Rotor Speeds: Pressure Limits Fuel Pressure Oil Pressure Installation Assumptions: Time Limited Dispatch ETOPS V. Operating and Service Instructions VI. Notes SECTION: ADMINISTRATIVE I. Acronyms and Abbreviations II. Certificate Holder Record III. Change Record TE.CERT European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 3 of 20

4 I. General 1. / Models: CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, CF34-8E6A1 2. Certificate Holder General Electric Aircraft Engines GE Aviation 1000 Western Avenue Lynn, Massachusetts USA 3. Manufacturer General Electric Aircraft Engines 4. Date of Application CF34-8C1 CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, CF34-8E6A1 16 October July Validation Reference Date: 1 May EASA Certification Date CF34-8C1 CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, CF34-8E6A1 29 June October 2002 EASA Certification for the CF34-8 engine models is granted, in accordance with Article 3 paragraph 1 (a)(i) of Commission Regulation (EU) No 748/2012, based on the CAA United TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 4 of 20

5 Kingdom validation letter issued following the JAA Validation Recommendation. It is recognised that Certification has previously been performed by a number of EU states. II. Certification Basis 1. FAA Certification Basis details: see FAA TCDS E00063EN 2. EASA Certification Basis: 2.1 Airworthiness Standards: For CF34-8C1: - JAR-E Change 9 21 October 1994 plus Orange Paper E/96/1 effective 8 August Orange Paper OP/E/97/01 December NPA-E-20 Birds 23 December NPA-E-27 Inclement Weather 16 September 1997 For CF34-8C5/-8C5A1/ - 8C5B1/ -8C5A2/ -8C5A3/ - 8E2/ - 8E2A1/ - 8E5/ - 8E5A1/ - 8E5A2/ - 8E6/ - 8E6A1: - JAR- E Change August NPA-E-20 Birds 3 December Special Conditions: SC1: Transient Overtemperature CF34-8C1 2.3 Equivalent safety finding: JAR E 890 (b) (1) Thrust Reverser Endurance Test 2.4 Deviations: None. 2.5 EASA environmental protection requirements: The environmental requirements are those implemented through EASA Basic regulation EASA Basic regulation EC (No.) 216/2008 as amended by (EU) No. 6/2013 and its implementing regulation (EU) No. 748/2012 annex Part 21, 21A.18 (b) as amended by (EU) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 5 of 20

6 No including CS-34. By reference the emissions regulations of Amendment 6 of ICAO Annex 16, Volume II become applicable. The regulatory emissions levels are those prescribed in Part III, Chapter 2, paragraph e) (CAEP/8) of the Annex. III. Technical Characteristics 1. Design Definition As defined by the applicable GE Model Lists See Note 6 2. Description Dual rotor, axial flow, high bypass ratio turbofan with single stage fan, ten stage axial compressor, annular combustion chamber, two stage high pressure turbine, four stage low pressure turbine, exhaust nozzle, starter, and a full authority digital engine control (FADEC). On the CF34-8E engine models only, a thrust reverser and aft core cowl is included in the engine type design. 3. Equipment Equipment are included in Design Definition. 4. Dimensions CF34-8C1 CF34-8C5 models CF34-8E models Overall Length 387 cm (152.3 inches) 388 cm (152.6 inches) 8 cm (121,2 inches) Overall Diameter cm (60.66 inches) cm (60.66 inches) cm (62.65 inches) See Note 1 5. Dry Weight CF34-8C1 CF34-8C5 models CF34-8E models Weight 1,227 kg (2,704 lb) 1,261 kg (2,780 lb) 1,428 kg (3,147.6 lb) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 6 of 20

7 6. Ratings Rating (see Note 2) CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 Takeoff ( min) (see (13790) (14510) (14510) (13790) (14510) Notes 3 and 4) Thrust kn (lb) Flat rate ambient temperature C( F) Normal Takeoff (5 min) (see Notes 3 and 4) Continuous Takeoff continuous (12670) (13277) (86.0) 25 (77) (13360) (13680) (86.0) (136) (13680) (86.0) (12670) (13280) (86.0) 25 (77) (14050) (13680) (86.0) Rating (see Note 2) CF34-8C5A3 CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 Takeoff ( min) (see (14510) (130) (130) (14510) (14510) Notes 3 and 4) Thrust kn (lb) Flat rate ambient temperature C( F) Normal Takeoff (5 min) (see Notes 3 and 4) Continuous Takeoff continuous (14510) (13680) (12410) (12540) (130) (12540) (13420) (13520) (14050) (13520) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 7 of 20

8 Rating (see Note 2) CF34-8E5A2 CF34-8E6 CF34-8E6A1 Take-off ( min) (see (14510) (14050) (14050) Notes 3 and 4) Thrust kn (lb) Flat rate ambient temperature C( F) Normal Take-off (5 min) (see Notes 3 and 4) Continuous Take-off continuous (14510) (13520) (13420) (13520) (14050) (13520) 7. Control System The engine is equipped with a Full Authority Digital Engine Control (FADEC) system. Software is verified to level A according to RTCA Document DO-178B System Component Fuel Metering Unit Woodward Governor 4120T01 Full Authority Digital Engine Lockheed/Martin 4120T00 Control (FADEC) Configuration Plug Hardware Engine Rating 2041M41 Engine Configuration M42 N1 Trim Setting M43 Ignition System 2 Ignition Exciters - Unison 9238M66 2 Ignition Plugs 4096T33 Federal Mogul / Champion Fuel Pump Argotech 4120T04 See Note Fluids 8.1 Fuel: Fuel conforming to GE Jet Fuel Specification No. D50TF2 is applicable for all models. See GEK (CF34-8C1/-8C5) and GEK (CF34-8E). Operating Instructions, for specific fuels approved per the subject specifications. TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 8 of 20

9 8.2 Oil: Oil conforming to GE Specification No. D50TF1 is applicable for all models. See GEK (CF34-8C1 & CF34-8C5) and GEK (CF34-8E models). Operating Instructions, for specific oils approved per the subject specifications. 9. Aircraft Accessory Drives Accessory Lube & Scavenge Oil Pump IDG Air Turbine Starter Hydraulic Pump CF34-8E Hydraulic Pump CF34-8C Alternator Fuel Pump Location on AGB Axis Axis-C Fwd Axis-C Fwd Axis-D Aft Axis-G Fwd Axis-G Fwd Axis-E Aft Axis-F Aft Speed, rpm Power (rated), kw (HP) Direction of rotation (facing AGB) (6) CCW (74.8) (*2) CW NA CW () () CW CW Torque Static/ Continuous/ Overload, Nm (lb-in) 33.9 (0) (*1) /5.4 (48) / NA 76.3 (675) (*1) / 67.5 (597) / (1129) (5 min) (*4) (1605) (5 sec) (*4) (2112), (4200) (*3) / NA / NA 64.7 (573) (*1) (*5) / 44.3 (392) / 75.7 (670) 64.7 (573) (*1) (*5) / 44.3 (392) / 75.7 (670) (4) CCW NA/NA/NA (40) CW (180) (*1)/ 34.23(3)/ NA Max. Acc. Wt, kg (lb) 4.67 (10.3) (81.2) (*6) (27.7) 6. (13.9) (dry) 6.67 (14.7) (dry) 1.36 (3.0) (23) Overhung Moment, Nm (lb-in) 3.73 (33) 81.3 (720) maximum 12.8 (113) 4.34 (38.4) 4.91 (43.5) Shear Torque, Nm (lb-in) ( ) ( ) ( ) (2004) maximum (2004) maximum 0.29 (2.6) NA (113) ( ) CW - Clockwise CCW - Counter Clockwise Accessory Speeds are based on Core Speed: rpm (*1) -40 C (-40 F) SLS TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 9 of 20

10 (*2) HP is constant over the operating range with slight variations due to changes in efficiency. HP extraction is 55.8 kw (74.8 HP) at 7898 rpm (pad speed) and 54.8 kw (73.5 HP) at 4618 rpm (pad speed). The 5 minute overload rating is 61.7 kw (82.7 HP) and the 5 second overload rating is 87.7 kw (117.6 HP) (*3) Nm (2112 in-lbs) at 15 C (59 F) SLS, Nm (4200 in-lbs) at -40 C (-40 F) SLS (*4) Overload at 4618 rpm (pad speed) (*5) 64.7 Nm (573 in-lbs) at 626 rpm (pad speed) (*6) Includes oil and V band coupling 10. Permissible Air Bleed Extraction: (See Note 5) Demonstrated Bleed Air (% of Total Compressor Massflow) Location CF34-8C1 CF34-8C5 CF34-8E Compressor Stage Compressor Stage 10 (Compressor Discharge) Allowable Bleed NA IV. Operating Limitations 1. Temperature Limits 1.1 Exhaust Gas Temperature C ( F): permissible temperatures are as follows: Inter-turbine temperature (T45), C ( F) The inter-turbine temperature is measured by 5 probes (5 thermocouples) or 10 probes (20 thermocouples) mounted in the low pressure turbine casing. ** For the CF34-8C1, Takeoff and maximum continuous T45 limits may be exceeded transiently as a result of OBV actuation provided T45 does not exceed 1021 C (1869 F) for seconds, and does not exceed a temperature limit that ramps from 1021 C (1869 F) to 979 C (1794 F) over the next seconds, as defined in GE Operating Instructions ~ GEK The total number of transient occurrences as a result of OBV actuation above a T45 of 979 C (1794 F) is limited to a maximum of 10 occurrences as defined in GE Engine Manual GEK TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 10 of 20

11 The 2-minute inter-turbine temperature (T45) limits (2 minutes out of 5 minutes take-off time), are intended to cover engine T45 overshoot characteristics which occur during engine stabilisation at constant Take-off thrust. Refer to GE Engine Manual GEK (CF34-8C1/-8C5), for inspection requirements when limits are exceeded. CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 Takeoff (5 minutes) 960 (1760) 990 (1814) 990 (1814) 990 (1814) Takeoff (2 min. out of a total of (1794) 1006 (1843) 1006 (1843) 1006 (1843) minutes) Normal Takeoff (5 minutes) 920 (1689) 947 (1736) 957 (1754) 948 (1738) Takeoff (2 min. out of a total of (1723) 963 (1765) 973 (1783) 964 (1767) minutes) Continuous 927 (1701) 960 (1760) 960 (1760) 960 (1760) At start up, ground 815 (1499) 815 (1499) 815 (1499) 815 (1499) 2 sec transient 955 (1751) NA NA NA 5 sec transient 927 (1701) NA NA NA At start up, air, assisted 815 (1499) 815 (1499) 815 (1499) 815 (1499) 2 sec transient 1010 (1850) NA NA NA 5 sec transient 993 (1819) NA NA NA At start up, air, windmill 927 (1701) 927 (1701) 927 (1701) 927 (1701) 2 sec transient 1010 (1850) NA NA NA 10 sec transient 960 (1760) NA NA NA TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 11 of 20

12 CF34-8C5A2 CF34-8C5A3 Takeoff (5 minutes) 990 (1814) 990 (1814) Takeoff (2 min. out of a 1006 (1843) 1006 (1843) total of 5 minutes) Normal Takeoff (5 minutes) 973 (1783) 990 (1814) Takeoff (2 min. out of a 989 (1812) 1006 (1843) total of 5 minutes) Continuous 960 (1760) 960 (1760) At start up, ground 815 (1499) 815 (1499) 2 sec transient NA NA 5 sec transient NA NA At start up, air assisted 815 (1499) 815 (1499) 2 sec transient NA NA 5 sec transient NA NA At start up, air, windmill 927 (1701) 927 (1701) 2 sec transient NA NA 10 sec transient NA NA CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 Takeoff 990 (1814) 990 (1814) 990 (1814) 990 (1814) (5 minutes) Takeoff (2 min. out of a 1006 (1843) 1006 (1843) 1006 (1843) 1006 (1843) total of 5 minutes) Normal Takeoff (5 minutes) 957 (1755) 990 (1814) 949 (1740) 973 (1783) Normal Takeoff (2 minutes out of a 973 (1784) 1006 (1843) 965 (1769) 989 (1812) total of 5 minutes) Continuous 960 (1760) 960 (1760) 960 (1760) 960 (1760) At start up, ground 815 (1499) 815 (1499) 815 (1499) 815 (1499) At start up, air assisted 927 (1701) 927 (1701) 927 (1701) 927 (1701) At start up, air, windmill 927 (1701) 927 (1701) 927 (1701) 927 (1701) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 12 of 20

13 CF34-8E5A2 CF34-8E6 CF34-8E6A1 Takeoff (5 minutes) 990 (1814) 990 (1814) 990 (1814) Takeoff (2 min. out of a 1006 (1843) 1006 (1843) 1006 (1843) total of 5 minutes) Normal Takeoff (5 minutes) 990 (1814) 966 (1771) 990 (1814) Normal Takeoff (2 minutes out of a 1006 (1843) 982 (1800) 1006 (1843) total of 5 minutes) Continuous 960 (1760) 960 (1760) 960 (1760) At start up, ground 815 (1499) 815 (1499) 815 (1499) At start up, air assisted 927 (1701) 927 (1701) 927 (1701) At start up, air, windmill 927 (1701) 927 (1701) 927 (1701) 1.2 Oil Temperature (measured in the oil tank) C ( F): All Models Continuous Operation 155 (311) Transient Operation (limited to 15 minutes) 163 (325) Transient operation above 155 (311) is limited to 15 minutes 1.3 Fuel Inlet Temperature (at engine fuel filter inlet) C ( F): All Models Continuous Operation: 121 (250) (Jet A, Jet A1, Jet B, JP8, JP5, JP4, JP4/JP5 (Mixture), Ground Operation) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 13 of 20

14 2. Permissible Rotor Speeds: takeoff Normal takeoff continuous Low pressure rotor (N1), rpm High pressure rotor (N2), rpm Low pressure rotor (N1), rpm High pressure rotor (N2), rpm Low pressure rotor (N1), rpm High pressure rotor (N2), rpm CF34-8C1 CF34-8C5 / -8E models Refer to GE Engine Manual GEK (CF34-8C1/8C5 models) and GEK (CF34-8E models) for inspection requirements when limits are exceeded. 100% N1 rotor speed is 7,400 rpm 100% N2 rotor speed is 17,820 rpm 3. Pressure Limits 3.1 Fuel Pressure At engine pump inlet: minimum pressure of 34 kpa (5 PSID) above the true vapour pressure of the fuel with a vapour liquid ratio of zero with aircraft boost operative. Operating range 34kPa (5 PSlG) to 345 kpa (50 PSIG). At engine motive flow discharge: minimum pressure of 1034 kpa (150 PSIG) at idle or above. Operating range is 1034 kpa (150 PSIG) to 5515 kpa (800 PSIG). See GE Installation Manual GEK (CF34-BC1/BC5), and GEK (CF34-8E). 3.2 Oil Pressure At idle on the ground, 172 kpa (25 PSID) minimum. At take-off 310 kpa (45 PSID) minimum to 656 kpa (95 PSID) maximum. Operating range, 172 kpa (25 PSID). See GE Installation Manual GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models). 4. Installation Assumptions: The installation assumptions are quoted in the GE Engine Installation Manuals: GEK (CF34-8C1 & CF34-8C5 models) GEK (CF34-8E models) TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 14 of 20

15 5. Time Limited Dispatch The engine is approved for Time Limited Dispatch as allowed by JAR-E 510(e)(2) and in accordance with 14 CFR Part 33, Amendment 20, Paragraphs 33.4 and The maximum rectification period for each dispatchable state is specified in the Airworthiness Limitations Section of the applicable CF34-8C1 & CF34-8C5 Engine Manual GEK and CF-34-8E Engine Manual GEK ETOPS Not applicable, not part of the engine certification basis V. Operating and Service Instructions CF34-8C1 & CF34-8C5 CF34-8E models Operating Instructions GEK GEK Installation Manual GEK GEK Engine Manual GEK GEK VI. Notes 1. Weight includes residual fuel and oil. 2. Engine ratings are based on calibrated test stand performance, and performance calculations are based on accepted parameter correction methods documented in the production data folder. These calculations assume the following conditions: 1. Static sea level standard conditions of 15 C (59 F) and kpa (29.92 inches Hg). 2. No aircraft accessory loads or air extraction. 3. No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. 4. Inlet bellmouth and cowl system as described in GE Installation Manual GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models). 5. Specified fuel having an average lower, heating value of 43,031kJ/kg (CF34-8C1/-8C5 models); 43,147 kj/kg (CF34-8E models) specified lube oil. 3. This engine is equipped with an automatic power reserve function for takeoff operation with one engine inoperative. During normal take-off, when the automatic power reserve function is activated, the engine control of the inoperative engine sends an input signal to the engine control of the operating engine. Upon receiving this signal, the engine thrust of the operating engine automatically increases from normal takeoff (NTO) or lower thrust to the corresponding, pre-determined maximum takeoff (MTO) thrust. If one engine is inoperable, full MTO thrust is available to the pilot at any time by throttle selection. The engine control system also incorporates schedules that assure a fully degraded engine, during operation at the NTO of lower thrust, will achieve the specified MTO thrust without exceeding the engine operating limits when the automatic power reserve function is activated. 4. The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating for that takeoff. The 5-minute takeoff time TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 15 of 20

16 limit may be extended to 10 minutes for one engine inoperative operation in multi-engine aircraft. 5. Refer to Operating Instructions GEK (CF34-8C1/8C5 models) and GEK (CF34-8E models) for engine warm-up procedure. 6. Refer to Operating Instructions GEK (CF34-8C1/8C5 models) and GEK (CF34-8E models) for thrust reverser operation. 7. Air Bleed Extraction - maximum customer air bleed extraction is as follows: Customer bleed air is available from either Stages 6 or 10 (compressor discharge) of the compressor at all operating conditions at or above idle. (No compressor bleed is permitted below idle). Customer bleed is scheduled to switch from Stage 10 bleed at low power operation to Stage 6 bleed at high power operation as described in GE Installation Manual GEK (CF34-8C1 & CF34-8C5 models), and GEK (CF34-8E models). 8. The maximum permissible inlet distortion is specified in GE Installation Manual GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models). Ground operational limits and procedures for operation in crosswind are specified in GE Specific Operating Instructions GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models). 9. This engine meets the applicable requirements for operation in icing conditions provided that for ground idle engine operation in icing conditions a minimum core speed N2 is maintained and for flight idle engine operations in icing conditions, an N2 to provide a minimum PS3 schedule as defined in GE Operating instructions GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models) are maintained. The FADEC Power Management controls ground and flight idle core speeds above the minimum speed demonstrated during engine certification for operation in icing conditions. At low ambient temperatures, the minimum permissible ground and flight idle speeds correspond to N2=58.47% (9,940 rpm) which is a non-adjustable limit, pre-set in the FADEC Power Management schedules. As ambient temperatures increase, the minimum permissible core speed increases as scheduled by the FADEC Power Management based upon N2 or PS3 control schedules. 10. For the CF34-8E models, the engine manufacturer supplies the Nacelle System. The following Aft Core Cowl and Thrust Reverser systems, which are a part of this Nacelle system, have been certified for the listed engine models under this TCDS in accordance with JAR-E. The JAR-E engine type design definition is provided by: Engine Model List Aft Cowl Core Parts List Thrust Reverser Parts List CF34-8E2 15F G0001 CF34-8E2A1 15F G0001 CF34-8E5 15F G0001 CF34-8E5A1 15F G0001 CF34-8E5A2 15F G0001 CF34-8E6 15F G0001 CF34-8E6A1 15F G0001 TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 16 of 20

17 11. The type definition for the CF34-8C1/-8C5 engine models does not include the thrust reverser. Compliance with JAR-E890 was demonstrated with the thrust reverser defined by: Model List TR CF34-8C1G01 Model List TR CF34-8C1 G02 Model List TR CF34-8C5G01 Model List TR CF34-8G5G02 Model List TR CF34-8C5A1G01 Model List TR CF34-8G5A1G02 Model List TR CF34-8C5B1G01 Model List TR CF34-8C5B1G02 Model List TR CF34-8C5A2G01 Model List TR CF34-8C5A2G02 Model List TR CF34-8C5A3G01 Model List TR CF34-8C5A3G02 (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) (Left Hand Nacelle/EBU) (Right Hand Nacelle/EBU) 12. Refer to Operating Instructions GEK (CF34-8C1/8C5 models) and GEK (CF34-8E models) for thrust reverser operation. 13. Life limits established for critical components, are published in GE Engine Manual GEK for CF34-8C1 & CF34-8C5 models and GEK for the CF34-8E models. 14. Recommended maintenance inspection intervals are published in GE Engine Manual GEK for CF34-8C1 & CF34-8C5 models and GEK for the CF34-8E models 15. The operating temperature limit for specific components and accessories specified in GE lnstallation Manuals GEK (CF34-8C1 & CF34-8C5 models) and GEK (CF34-8E models), must be observed when installing the engine. 16. Static thrusts at sea level are rated at C ambient temperature and below for takeoff and at 25 C and below for maximum continuous. The computer performance deck for calculating engine performance is as follows: Engine Model CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C581 CF34-8C5A2 CF34-8C5A3 CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E6 CF34-8E6A1 Computer Deck No. L0073A5 G0175C G0175C L0073A G0175C G0175C G0175D G017SD G0175D G0175D G017SD G0175D G0175D TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 17 of 20

18 17. Overhaul of the CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), components is only authorised via approved component manuals 18. Effective September 10, 2010 the model designations CF34-8D1, CF34-8D3, CF34-8D5 and CF34-8D6 were withdrawn at the request of the manufacturer. These models were originally recognised based on validations performed in several EU member states following the Validation Recommendation by the JAA. None of these models were released to revenue service. 19. A suffix may be added to CF34-8 basic engine model numbers on the engine nameplate to identify minor variations in the engine configuration, installation components, or differences specific to aircraft requirements, for example, CF34-8C5/B or CF34-8C5/M. Service Bulletin (SB) 72-A0237 describes the conversion of the base model to a suffix designation (with /B designation) and Service Bulletin (SB) 72-A0243 describes the conversion from the suffix designation (with /B designation) back to the base model. Service Bulletin (SB) describes the conversion of the base model to a suffix designation (with /M designation) and Service Bulletin (SB) describes the conversion from suffix designation (with /M designation) back to the base model. Only those designations and purposes listed below may be used. The SB number must be appended to the engine nameplate Life limits for the /B and /M minor model designations, established for critical components, are published in Authority approved GE Engine Manual GEK (CF34-8C1/8C5 models): Designation: CF34-8C5/B CF34-8C5B1/B CF34-8C5A1/B CF34-8C5A2/B Purpose: Indicates use of the engine in an Alternate Mission application, with associated airworthiness limitations section life limits. Indicates use of the engine in an Alternate Mission application, with associated airworthiness limitations section life limits. Indicates use of the engine in an Alternate Mission application, with associated airworthiness limitations section life limits. Indicates use of the engine in an Alternate Mission application, with associated airworthiness limitations section life limits. TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 18 of 20

19 CF34-8C5/M CF34-8C5A1/M CF34-8C5A2/M Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating with associated airworthiness limitations section life limits. Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating with associated airworthiness limitations section life limits. Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating with associated airworthiness limitations section life limits. TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 19 of 20

20 SECTION: ADMINISTRATIVE I. Acronyms and Abbreviations n/a II. Certificate Holder Record n/a III. Change Record Issue Date Changes TC issue Issue April 2015 Initial Issue Initial Issue 22 April 2015 Issue March 2017 Administrative correction in section 6 Ratings 16 March END- TE.CERT.XXXXX-001 European Aviation Safety Agency, All rights reserved. ISO9001 Certified. Page 20 of 20